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EFFECTIVITY 28-20-00 Page 3
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 129
ALL
MAIN FUEL PUMP SYSTEM COMPONENTS
AIR RELEASE VALVE
IDENTIFICATION
FIN: 86QM, 87QM
LOCATION
ZONE: 540, 640
COMPONENT DESCRIPTION
It allows air, but not fuel, to be expelled from the
pipeline and prevents air being sucked in.
TMUFUEK01-T02 LEVEL 3
EFFECTIVITY 28-20-00 Page 4
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 130
ALL
TMUFUEK01-P02 LEVEL 3
MAIN FUEL PUMP SYSTEM COMPONENTS - AIR RELEASE VALVE
EFFECTIVITY 28-20-00 Page 5
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 131
ALL
MAIN FUEL PUMP SYSTEM COMPONENTS
SEQUENCE VALVES
IDENTIFICATION
FIN: None
LOCATION
ZONE: 540, 640
COMPONENT DESCRIPTION
The SEQUENCE VALVES are pressure relief valves attached
to secondary outlets on wing tank pumps only.
TMUFUEK01-T03 LEVEL 3
EFFECTIVITY 28-20-00 Page 6
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 132
ALL
TMUFUEK01-P03 LEVEL 3
MAIN FUEL PUMP SYSTEM COMPONENTS - SEQUENCE VALVES
EFFECTIVITY 28-20-00 Page 7
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 133
ALL
MAIN FUEL PUMP SYSTEM COMPONENTS
CENTER TANK FUEL PUMP
IDENTIFICATION
FIN: 37QA, 38QA
LOCATION
ZONE: 140
COMPONENT DESCRIPTION
The pump delivers fuel at 11000 lb/hr (4989kg/hr) at
30 psi (2.08 bar). Thermal fuse: 200 degrees C.
The pump is installed in a canister containing a slide
valve so that the pump can be removed without having
to drain the tank.
TMUFUEK01-T04 LEVEL 3
EFFECTIVITY 28-20-00 Page 8
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 134
ALL
TMUFUEK01-P04 LEVEL 3
MAIN FUEL PUMP SYSTEM COMPONENTS - CENTER TANK FUEL PUMP
EFFECTIVITY 28-20-00 Page 9
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 135
ALL
MAIN FUEL PUMP SYSTEM COMPONENTS
CENTER TANK FUEL PUMP REMOVAL INFORMATION
IDENTIFICATION
FIN: 37QA, 38QA
LOCATION
ZONE: 140
COMPONENT DESCRIPTION
PUMP REMOVAL:
- disconnect electrical connector
- remove attachment bolts
- use extractor screws in removal holes
- drain it
- turn the pump
- pull it out
TMUFUEK01-T05 LEVEL 3
EFFECTIVITY 28-20-00 Page 10
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 136
ALL
TMUFUEK01-P05 LEVEL 3
MAIN FUEL PUMP SYSTEM COMPONENTS - CENTER TANK FUEL PUMP REMOVAL INFORMATION
EFFECTIVITY 28-20-00 Page 11
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 137
ALL
MAIN FUEL PUMP SYSTEM COMPONENTS
WING TANK FUEL PUMP
IDENTIFICATION
FIN: 21QA, 25QA, 22QA, 26QA
LOCATION
ZONE: 540, 640
COMPONENT DESCRIPTION
Sequence valve reduces pump outlet pressure to 25 psi.
The pump is installed in a canister containing a slide
valve so that the pump can be removed without having
to drain the tank.
TMUFUEK01-T06 LEVEL 3
EFFECTIVITY 28-20-00 Page 12
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 138
ALL
MAIN FUEL PUMP SYSTEM COMPONENTS - WING TANK FUEL PUMP
TMUFUEK01-P06 LEVEL 3
EFFECTIVITY 28-20-00 Page 13
Apr 30/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 28 FUEL SYSTEM
UF94200
EFFECTIVITY Page 139
ALL
MAIN FUEL PUMP SYSTEM COMPONENTS
WING TANK FUEL PUMP REMOVAL INFORMATION
IDENTIFICATION
FIN: 21QA, 25QA, 22QA, 26QA
LOCATION
ZONE: 540, 640
COMPONENT DESCRIPTION
PUMP REMOVAL:
- disconnect electricalconnector
　
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